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Calculation of the pressure distribution over a wing at sonic speeds

K. W. Mangler (1951)

A method is developed for the calculation of the pressure distribution and the aerodynamic forces and moments acting on a wing at incidence, a wing in (steady) roll and a wing in (steady) pitch. The calculation is based ...

The aerodynamic derivatives with respect to a rate of yaw for a delta wing with dihedral and at incidence at supersonic speeds

J. H. Hunter-Tod (1951)

Expressions are developed on the basis of an unsteady flow analysis for the yawing derivatives for a delta wing with small dihedral at small incidence flying at supersonic speeds. The assumptions of the linearised theory ...

Theoretical load distribution on a wing with a cylindrical body at one end

J. Weber (1952)

A method is derived for calculating the spanwise load distribution over a lifting wing having a long circular-cylindrical body at one end. The solution is derived for arrangements giving constant induced downwash, but can ...

An examination of the flow and pressure losses in blade rows of axial-flow turbines

D. G. Ainley; G. C. R. Mathieson (1951)

The design of axial-flow turbines has been hampered in the past by a lack of comprehensive data regarding pressure losses and gas deflections through rows of turbine blades. In the present report much of the available ...

The reduction to standard conditions of take-off measurements on turbo-jet aircraft

G. Jackson; K. J. Lush (1951)

Summary.--A reduction method intended for routine use is derived whereby the take-off distance required for a turbo-jet aircraft to clear a 50-ft screen under a specified set of standard conditions of air temperature and ...

An experimental investigation of a thick-aerofoil nozzle cascade

S. J. Andrews; N. W. Schofield (1950)

The cascade tests on a thick-aerofoil turbine nozzle bla~te suitable for a cooled turbine show that it has a good performance over a wide incidence range up to M = 0.8. Above this value the loss coefficient rises and does ...

Methods for calculating the lift distribution of wings subsonic lifting-surface theory

H. Multhopp (1950)

This report contains some fairly simple and economic methods for calculating the load distribution on wings of any plan form based on the conceptions of lifting-surface theory. The computer work required is only a small ...

Tests on a 'glauert' nose-suction aerofoil in the N.P.L. 4-ft. no. 2 wind tunnel

F. Cheers; Ola Douglas (1947)

Tests on an 8.65 per cent thick nose-suction aerofoil designed by Glauert have been made in the 4 ft No. 2 wind tunnel at the National Physical Laboratory at Reynolds numbers 0.385 and 0.577 x l0 (to the power of 6). The ...

Multhopp's subsonic lifting-surface theory of wings in slow pitching oscillations

H. C. Garner (1952)

A draft of this theory was completed by H. Multhopp during 1950, before he left the Ministry of Supply. It has been edited by the writer, who is responsible for the calculated examples. This report is an extension of ...

Low-Speed Tests on 45-deg Swept-back Wings Parts I and II

J. Weber; G. G. Brebner; D. Kuchemann (1951)

PART I - Pressure Measurements on Wings of Aspect Ratio 5. This report contains the results of pressure measurements on three 45-deg swept-back wings with constant chord and aspect ratio 5, over an incidence range up to ...

The secondary flow in curved pipes

H. G. Cuming (1952)

The Navier-Stokes equations for the flow of a viscous incompressible fluid through curved pipes of different sections are solved in power series of the curvature of the pipe. The solution is given as far as the first power ...

An experimental investigation of stress diffusion in non-buckling plates

L. H. Mitchell (1952)

The purpose of this report is to provide experimental resuKs for comparison with theoretical analyses of stress diffusion problems. The structures considered consist of plane reinforced sheet which has been assumed not to ...

Wind-tunnel tests on the NPL 434 nose-slot suction aerofoil

J. Williams; R. C. Pankhurst; Edna M. Love (1952)

Stalling tests were made on the 8 per cent thick section NPL 434, which has been specially designed for nose-slot suction. At the higher suction quantities, the maximum lift of the aerofoil was considerably greater than ...

Permissible design values and variability test factors

R. J. Atkinson (1950)

For the design of structural elements it is postulated that:- (a) not more than 10 per cent to any given design should have strength below the design value (b) not more than 0.1 per cent should have strength below 90 per ...

Evaporation from the Surface of a Body in an Airstream (With Particular Reference to the Chemical Method of Indicating Boundary-layer Transition)

P. R. Owen; A. O. Ormerod (1951)

The problem of predicting the rate of transport of a gas from or into the surface of a two-dimensional body in an airstream is discussed. The principal object of the investigation is to provide a means of estimating the ...

Determination of the stress distribution in reinforced monocoque structures Part 1 A theory of flat-sided structures

L. S. D. Morley (1951)

This paper is concerned with the formation of basic differential equations for the determination of the stress distribution in reinforced monocoque flat-sided structures, such as rectangular or polygonal fuselages and wing ...

Control testing in wind tunnels

L. W. Bryant; H. C. Garner (1951)

If ad hoc wind-tunnel work on controls is to be of value it is essential that the same precautions should be taken as are necessary for fundamental research. For the model there must be careful selection of material and ...

Tests on a 'lighthill' nose-suction aerofoil in the N.P.L. 4-ft. no. 2 wind tunnel

F. Cheers; W. G. Raymer; Ola Douglas (1947)

A series of tests on an 8.6 per cent thick nose-suction aerofoil designed by Lighthill has been made in the 4 ft No. 2 Wind Tunnel at the National Physical Laboratory at Reynolds numbers of 0.385 and 0.577 x 10(to the power ...

Experiments in the compressed air tunnel on swept-back wings including two delta wings

R. Jones; C. J. W. Miles; P. S. Pusey (1948)

The experiments considered in the present report form part of an investigation into the characteristics at high values of Reynolds number, of swept-back wings, particularly swept-back wings of triangular plan form, commonly ...

An extension of Multhopp's method of calculating the spanwise loading of wing-fuselage combinations

J. Weber; D. A. Kirby; D. J. Kettle (1951)

A simple method is described for calculating the spanwise loading over wing-fuselage combinations. It is based on Multhopp's method, which is extended here to cover wings of finite thickness, large root chords compared ...

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